Propeller



` SeptA 23, 1930. s. TQ CARTER Y l PROPELLER 4 sheets-sheet Filed May 1928 ww l Q z:

INVENToR..

Byykwv 7,4 3 ATTORNEYS.

Sept. 23, 1930. I T, CARTER i n 1,776,650

PROPELLER Filed May 8, 1928 4 Sheets-$heet 2 SepLZB, 1930. Y s. T. CARTER r i 1,776,650

Y PROPELLER Filed May '8, 1928 4 Sneetswsnet 3 W4; ATTORNEYS.

Sept. 23,193@ s. T; CAR-m 1376,65@

PROPELLER Filed may 8. 1928 4 'shee-sneei 4 of the bla Patented Sept. 23,-'1930 PATENT ori-lcs SIDNEY T. OF PABNASSUS', PENNSYLVANIA' PBOPELLER Appleman med my' s, 192s. semi No. 218,047.

'This invention relates to propellers and more particularly to air propellers such as are em loyed on aeroplanes and the like.

An o ject of this invention'is to provide 5 a device of the type set forth constructed and arranged so as to permit changes in the pitch of the 'propeller blades.

' A further object is to provide a propeller for aeroplanes of such construction and arrangement as to enable the direction of thrust to be changed at will.-

A still further object is to provide, a device' of the type set forth of rugged 'construction and `which Awill be effective and reliable in.

operation and relatively ture and assemble.

'These and other objects which will be apparent to those skilled in this particular art are accomplished by'means of the invention illustrated in the accompanying drawings in which Figure 1 is a transverse sectional view through a` ortion of a propeller mechanism constructed) in accordance with one embodiment of this invention. Fig. 2 is a partial sectional view on the line 2-2 of Fig. 1. Fig. 3 is a transverse sectional view on the line 3-3 of Fig. 1. Fig. 4 is a view `similar tc cheap to manufac- Fig. 1 of, a ropeller constructed in accordance with a Herent embodiment 'of the present invention. Fig. 5 is a transverse-sectional 'view on the line 5--5 of Fig. .4. Fig. 6 is a similar view on the line 6-6 of Fig. 4, and Fig. 7 is a sectional view on the line 7-7 of ''he particular embodiments of this invention which have been chosen for the purposes of illustration include a propeller having oppositely extending blades which are associated with a rotatmg shaft so as to be operated thereb in the'usual manner. The blades are movabl'y supported in suitable socket members and are adaptted tobe rotated on their axes so as to shi or reverse the itch thereof. Suitable mechanism is provide for and arranglement that the direction ofthrust es is indicated thereby. By providing a propeller having blades the .pitch lio of whichls reversible'at T. ill, the' direction controlling the position of the blades and this control mechanism is of such construction of thrust of the blades can be reversed upon landing so as to bring the plane to a stop more quickly thanis possible with the usual form of propeller.

As illustrated in' Fi s, 1 to 3, the particular embodiment of t e invention, therein shown, includes a stationary casing 10l through which a rotatable propeller shaft 11 projects. Oppositely extending ropeller blades 12 are rigidly secured to soc et members 13 which are rotatably supported vin diametrically opposed socket recesses 14 formed in a rotating frame 15 which is rigidly mounted on the projecting end of the rotatable shaft 11 for 'rotation therewith. Suitable mechanism is provided for rotat-` ing orshifting the socket members 13 in the socket recesses 14 for the pur ose of changin the 'pitch of' the propeller lades mounte therein.

As illustrated, this mechanism includes a blade shifting arm 16 projecting rearwardtating housing 15. Each arm 16 has separate and spaced segmental gears 17 and 18 respectively. An annular blade shitftimJr member 19, having diametrically op ose gear sections'20` formed .on opposite s cul-1l ders 21, is'rotatably mounted on the inner face of an annular inwardly extending, retaining ange 22 formed around the 1nner ly from each socket member within the ro- Y edge of the rotating frame. Each segmental ear section 20 of the blade shifting memer engages a. gear 23 secured to a pin 24` on which is also mounted a gear 25 engaging the segmental gears 17 o the associated blade shifting arms 16. The other segmental gears 18 of each arm mesh withAv diametrically o posed geared sections -26 formed on a lade shifting member 27 mounted on a supporting portion 28 ofthe rotiltlin frame.

may be turned about their respective longitudinal axes in'o posite directions where Vy the pitch of the ades can be reversed at willaccording to the conditions 'arising in the flight of the airplane.

Each blade control ing or rotating` memlade shifting members 19 and 27 I' are so arranged -that the propeller blades 1 y vinner brake face 29 ber 19 and 27 normally rotates with the rotating frame and associated mechanism. When it is desired to shift the blade from one position to another to change the pitch thereof, it will be apparent that this can be accomplished during operation of the pro-v peller by retarding the movement of one or the other of the control members so as to cause relative rotation between one or the other of such members and the rotating frame and blade shifting arms. As illustrated in Figs. 1 andA 3, this is accomplished by providing each control member with an which, when the pitch of the blades is to be changed, frictionally engages a brake mechanism associated with the control member 19. In this manner the blade pitch can be instantly changed at any desired moment by actuating one of the brake mechanisms associated with either of the control members, depending upon what change it is desired to make in the blade itch. Suitable mechanism is also provided or selectively operating either brake. As 'illustrated in Figs. l and 3, annular brake shoes 30 have ears 31 extending into a recess 32 formed in the stationary frame 10' and supported on an associated pin 33 connecting the ears of the separate shoes' together for maintaining them in cooperating relationship. The shoes are supported upon the central frame by suitable springs 34 and a spring 35 is associated with the upper ends of the shoes for normally throwing them into inoperative posit-ion. The shoes are adapted to be spread into braking engagement with the associated control member by pressure pistons 36 associated with the upper end of each brake shoe and mounted 1n a pressure cylinder 37 adapted to receive fluid pressure through a line 38 from a cylinder 39 having a piston 40 associated therewith. The pressure cylinder 41 of the brake mechl anism associated with the control member 27-is connected by line 42 to a pressure cylinder 43 having an operating piston mechanism 44. A brake operating lever 45 -is mounted upon a pin 46 so as to actuate either one or the other of the brake mechanisms, depending upon the direction in which the lever is oscillated. The oscillation of the lever in either direction will operate one or the other of the brake mechanisms.,y A brakelining 47 is associated with each of the brake mechanisms.

In operation, assuming the propeller shaft to be operating the propeller so as to vdrive the associated plane, and the propeller blades are positioned so that the blade shifting arms 16 are in an extreme position, as illustrated in Fig. 2, for providing the pitch desired for`propelling purposes, and assuming that it is desirable to reverse the pitch of the blades in order to come to a quick stop upon landing, the brake operating lever 45 will be moved in a direction to operate the brake mechanisms associated with the control lnember 19. The latter is, of course, rotating with the frame, blades, and associated mechanism. After the brake is applied the speed of rotation of the control member is slowed up, causing relative movement between it and the rotating frame, in turn causing the gears 23 and 25 to rotate and throw the blade shifting arms 16 to the other position through an angle such as to shift the pitch of the blades. This change results in a reversal of the pitch of the blades and stopping of the plane within a relatively few feet. It will be readily understood that the blades may be shifted in the other direction so as to return the pitch thereof to normal by moving the lever 45 in the opposite direction so as to actuate the brake mechanism associated with the other control member 27. It will also be apparent that the portions of the rotating frame with which the arms 16 Contact when in their eXtreme positions `constitute stops by determining the positions of the blades (see Fig. 2).

In Fig. 2, the segmental gear .is in contact with one Wall of the casing or frame 15 which acts as a stop to limit the movement of the blades when the pitch t-hereof is changed in one direction. If the segmental gear 16 is turned in the opposite direction (or in-a clockwise direction with reference to Fig. 2) the gear 16 will come in contact with the frame or casing 15 and stop thereby preventing further change in the pitch of the propeller blades.

In the embodiment illustrated in Figs. 4 to 7 the rotating frame 5() secured to the propeller shaft has diametrically opposed socket recesses 51 in which the blade sockets 52 are rotatably mounted. The blade sockets are adapted to be rotated in the recesses by blade shifting Worms 53 mounted on worm shafts 54 and engaging segmental worm wheels 55 for rotating the bladesockets 52 relatively to the recesses 51 and thus changing the pitch of the blades, and the one segment is so arranged that, when in one extreme position, the pitch of the blades is such that their thrust is effective in one direction, while when the segment is in the other eXtreme position, the thrust is in the opposite direction. The two extreme positions are determined by suitable stops 56. Each blade shift-ing worm shaft projects out-i wardlly through the rotating frame and the projecting end of each shaft is provided with an actuating gear 57 meshing with a gear 58 secured to the propeller shaft and also meshing with an annular gear 59 surrounding the Worm operating gear 57 as illustrated in Figs. 4 and 6. A brake mechanism 60 is associated wit-l the outer surface of the annular gear 59 for the purpose of causing relative rotation between 'such gear and the rotating frame includingV the spur gear 58 so as to rotate the illustrated, this mechanism includes a brake lever 61 mounted on a pivot pin 62 for contracting or expanding the brake band 63. The

brake lever 61 is operated so as to a ply the brake tothe gear 59 by drawin on t e cable 64. A brake' wheel 65 is forme as a part of, or connected to, the inner spur gear 58 and a brake mechanism 66 adapted to be actuated by an operating cable 67 is associated 'therewith for causing relative movement between the spur gear 58 and the rotating frame so as to rotate the worm gears 57 and worms58 in the direction opposite to that caused by operation of the brake mechanism 60.

It will be apparent that the blade pitch is changed in this arrangement by operating one or the other of the brake mechanisms 60 or 66 for the purpose of rotating the worm operating gears 5 and associated worms 53 1n one direction or the other. The brake cables 64 and 67 can be operated b any suitable mechanisms (not shown) suc as will be readily understood by any mechanic.

, the blades is such t It will also be a parent that the pitch of lat o eration of the propeller tends to move theY lade shiftingarms against the associated stops which determine the extreme positions of the blades.

Although I have described in detail certain specific embodiments of this invention, it will be apparent that various changes, additions,

omissions vvand 'substitutions can be made therein without departing from the spirit of this invention or the scope of the appended claims.

What I claim asnew and desire to secure 1. The combination in a propeller of a rotating frame provided with outwardly extending blades, an arm associated with each of saidD blades for rotating the same so as to reverse the pitch thereof, stops for limiting the movement of said arm in each direction and positioned so that operation of said propeller forces said arm against one or the other of said stops, and means for determining the eective direct-ion of operation of said blades.

2. The combination 1n a propeller of a blade mounted for rotation about its axis, a geared segment secured to said blade for rotating the same, operating mechanism geared to said segment for moving said blade in one direction 'or the other to change the pitch thereof, frictional mechanism for movlng said ysegment in one direction, another frictional mechanism for movin said segment in the other direction, stops or limiting the movement of saidse ent in each direction and means for selectively operating either of said frictional mechanisms.

3. The combination in a propeller of a rotating frame having blades movably mounted therein, a blade moving segment associated with eachof said blades, a gear rotatable with said frame, means for causing relative movement between sa1d gear and'said frame forA ments in one direction or the other` to reversethe pitch of vsaid blades.

5. In a reversible propeller, .in combination, a propeller shaft, a propeller support on the shaft,(propeller blades mounted in said support,'sai propellers being disposed for turning about their longitudinal axes, each propeller havin a gear and a worm for turning the same a out its longitudinal axis, a pinion for each worm, and two concentric gears turnably mounted on said shaft, said pinions meshing with saidv gears.

6. In a reversible propeller, in combination, a propeller shaft, a propeller support on the shaft, propeller blades mounted in said support, said propellers being disposed for turning abouttheir longitudinal axes, each propeller having a gear and a worm for turning the same about its longitudinal axis, a pinion for each worm, two concentric gears turnably mounted on said shaft, said pinions meshing with said gears, and brake mechanism for each of said concentric gears for eifecting relative movement between saidA DIISOI-AI MER 1,776,650.4-Sz'dney T. Carter, Parnassus, Pa. PROPELLER. Patent dated September 23, 1930. Disclaimer led June 24, 1932, by the assignee, Bendix Aviation Corporation. Hereby enters this disclaimer to that part of the claims in said specification Which are in the following Words, to Wit:

5. In areversible propeller, in combination, a propeller shaft, a propeller support j on the shaft, propeller blades mounted in said support, said propellers being disposed 'for turning about their longitudinal axes, each propeller having a gear and a Worm for turning the same about its llongitudinal axis, a pinion for each Worm, and two concentric gears turnably mounted on said shaft, said pinions vmeshing with said gears.

6. In a reversible propeller, in combination, avpropel'ler shaft, a propeller support on the shaft, propeller blades mounted in said support, said propellers being disposed 'for turning about their longitudinal axes, each propeller having a gear and a Worm for turning the same about "its longitudinal axis, a pinion for each Worm, two concentric gears turnabbT mounted on said shaft, said pinions meshing with said gears, and brake mechanism for each of said concentric gears for effecting relative movemnt between said gears and shaft, whereby the pitch of said propellers may be reverse [Oficial Gazette July 1.9, 1932.] 

